An experimental investigation of the design variables for NACA submerged duct entrances

Information concerning the parameters and design variables affecting an NACA submerged duct design is presented

NACA Research Memorandums

Report presenting an experimental investigation of a submerged air inlet incorporating a cascade of airfoils for turning and diffusing the entering air. Variables associated with submerged air inlets and airfoil-cascade designs were considered, including changes to the ramp plan form and angle for the submerged inlet and the cascade-axis inclination, cascade-blade angle, solidity, and inclination of the center line of the duct for the cascade

NACA Research Memorandums

Information concerning the parameters and design variables affecting an NACA submerged duct design is presented

NACA Advanced Confidential Reports

The results of a preliminary investigation of submerged duct entrances are presented. It is shown that an entrance of this type possess desirable critical speed and pressure recovery characteristics when used on a fuselage or nacelle in a region of low incremental velocity and thin boundary layer. The data obtained indicate that submerged entrances are most suitable for use with internal-flow systems which diffuse the air only a small amount: for example, those used with jet motors which have axial-flow compressors. Where complete diffusion of the air is required, fuselage-nose or wing leading edge inlets may prove to be superior. The results of the investigation have been prepared in such a form as to permit their use by a designer and the application of these data to a specific design is discussed

An experimental investigation of the design variables for NACA submerged duct entrances /

Includes bibliographical references.Mode of access: Internet